知搜-全球专利检索

  1. 登录
  2. 注册

搜索结果

16 条记录 (耗时 0.019 秒)

    Component joint
    1.
    发明授权
    Component joint 有权

    公开(公告)号：US10731492B2

    公开(公告)日：2020-08-04

    申请号：US15373130

    申请日：2016-12-08

    申请人： MTU Aero Engines AG

    发明人： Alexander Kloetzer ,  Manfred Feldmann

    IPC分类号： F01D11/00 ,  F01D25/24 ,  F16B37/12 ,  F16B33/00 ,  F04D29/08 ,  F02C7/28 ,  F01D25/28

    摘要： A component joint including a turbomachine component (10) having at least one component flange (11); a mating turbomachine component (20) connected thereto and having at least one mating component flange (21); and at least one seal (30) to provide a seal against an overpressure (p2−p1) on the component side, the at least one seal (30) having a sealing surface (31) that engages into a groove (12) of the turbomachine component (10), the groove (12) being disposed on a mating-component-flange-facing side of the component flange (11) and having a contact surface (13) for sealingly axially supporting the sealing surface (31).

    Arrangement for joining elements of turbomachines
    2.
    发明授权
    Arrangement for joining elements of turbomachines 有权

    公开(公告)号：US10518368B2

    公开(公告)日：2019-12-31

    申请号：US15341270

    申请日：2016-11-02

    申请人： MTU Aero Engines AG

    发明人： Alexander Kloetzer ,  Manfred Feldmann

    IPC分类号： F01D25/24 ,  B23P15/04

    摘要： The present invention relates to an arrangement, comprising a first turbomachine element with a first turbomachine element through-opening, a second turbomachine element, a sliding element with a sliding element through-opening that is arranged, at least in part, in the first turbomachine element through-opening, a sleeve that engages through the sliding element through-opening along a through-axis, and a fastening member that engages through the sleeve for fastening the sleeve to the second turbomachine element. Furthermore, the invention relates to a method for fastening the first turbomachine element to the second turbomachine element, a turbomachine with the above-mentioned arrangement, and use of this arrangement.

    Rotor of a turbomachine
    4.
    发明申请
    Rotor of a turbomachine 审中-公开
    涡轮机转子

    公开(公告)号：US20150139808A1

    公开(公告)日：2015-05-21

    申请号：US14546699

    申请日：2014-11-18

    申请人： MTU Aero Engines AG

    发明人： Alexander Kloetzer ,  Dieter Hofmann

    IPC分类号： F01D5/30

    CPC分类号： F01D5/3038 ,  F01D5/32

    摘要： A rotor of a turbomachine. The rotor includes at least one blade (4, 6, 8) that has a blade leaf (20) and a blade root (54, 55, 58), and a rotor base body (2), in particular a disk (2), that has an outwardly open, circumferential groove (12) for receiving the blade root (54, 55, 58). The circumferential groove (12) and the blade root (54, 55, 58) are shaped in a way that allows the blade root (54, 55, 58) to be secured in the circumferential groove (12) by the rotation of the blade (4, 6, 8) about an axis (Ar, AT).

    摘要翻译： 涡轮机的转子。 转子包括具有叶片叶片（20）和叶片根部（54,55,58）和转子基体（2），特别是盘（2）的至少一个叶片（4,6,8） ，其具有用于接收叶片根部（54,55,58）的向外开口的圆周凹槽（12）。 圆周沟槽（12）和叶片根部（54,55,58）的形状可以通过叶片的旋转将叶片根部（54,55,58）固定在周向槽（12）中， （4,6,8）围绕轴线（Ar，AT）。

    Seal arrangement for turbine
    5.
    发明授权
    Seal arrangement for turbine 有权

    公开(公告)号：US10533665B2

    公开(公告)日：2020-01-14

    申请号：US15453672

    申请日：2017-03-08

    申请人： MTU Aero Engines AG

    发明人： Alexander Kloetzer

    IPC分类号： F16J15/3288 ,  F01D11/02 ,  F02C7/28 ,  F16J15/16

    摘要： The invention is directed to a seal arrangement, in particular a brush seal, for a turbine, in particular an aircraft gas turbine, with a sealing element and with a sealing surface that interacts with the sealing element, wherein the sealing element and the sealing surface are arranged concentrically with respect to each other, in particular concentrically around a machine axis of the turbine is hereby characterized in that the sealing element and the sealing surface are designed in such a way that, in a first operating state, a gap is formed between them, and in that, in a second operating state, a sealing contact is produced between the sealing element and the sealing surface.

    BLADE-DISC ARRANGEMENT FOR A TURBOMACHINE
    6.
    发明申请
    BLADE-DISC ARRANGEMENT FOR A TURBOMACHINE 审中-公开

    公开(公告)号：US20190010825A1

    公开(公告)日：2019-01-10

    申请号：US16027635

    申请日：2018-07-05

    申请人： MTU Aero Engines AG

    发明人： Alexander Kloetzer

    IPC分类号： F01D25/08

    摘要： The present invention relates to a blade-disc arrangement for a turbomachine having a disc and a plurality of grooves that are arranged in a casing surface of the disc for taking up blades, as well as a plurality of blades with blade roots that are accommodated in the grooves, wherein at least one heat shield element is arranged between at least one blade root and a groove surface of at least one groove, so that there is no direct contact between blade root and disc in the groove region, wherein the heat shield element is formed of a ceramic material, at least in part.

    Blade-disk assembly, method and turbomachine
    7.
    发明授权
    Blade-disk assembly, method and turbomachine 有权

    公开(公告)号：US10041363B2

    公开(公告)日：2018-08-07

    申请号：US14546675

    申请日：2014-11-18

    申请人： MTU Aero Engines AG

    发明人： Werner Humhauser ,  Herman Klingels ,  Alexander Kloetzer

    IPC分类号： F01D5/30 ,  F01D5/14 ,  F01D5/32

    CPC分类号： F01D5/3038 ,  F01D5/147 ,  F01D5/32 ,  F05D2230/60 ,  Y10T29/49321

    摘要： A blade-disk assembly of a turbomachine is provided, the blade-disk assembly having a plurality of adjacent rotor blades and a closure blade which are tilted into an anchoring groove, and at least one circumferential retention element which interlockingly cooperates with at least one blade, as well as a plurality of tilt-out prevention elements which are disposed between the groove base and the root portions and which, in the rest state, space the blades from the groove base when in the upper position. The blade-disk assembly further has a locking element, a portion of which is located between the groove base and the root portions and which, in the rest state, spaces the closure blade from the groove base when in the upper position. A method for assembling such a blade-disk assembly, as well as a turbomachine, is also provided.